A motion heat transfer test system and method for spacecraft vacuum thermal testing

Abstract

The application relates to the technical field of spacecraft vacuum thermal test, and provides a motion heat transfer test system and method for spacecraft vacuum thermal test. The system comprises: a dynamic plate which is attached with heating sheets and can provide adjustable heat consumption power for simulating product heat consumption effects; a static plate which is movably connected with the dynamic plate and is formed with a nested convex structure, the dynamic plate can make reciprocating motion relative to the static plate when the dynamic plate is driven; a driving end which comprises a torque sensor, a telescopic motor and an adapter push rod, the adapter push rod is connected with the hot end dynamic plate to drive the dynamic plate to make reciprocating motion relative to the static plate; and a heat dissipation support structure which comprises a cold plate support, a cold plate support column and a liquid nitrogen cold plate; the heat dissipation efficiency of the hot end dynamic plate is adjusted by controlling and adjusting the motion frequency of the dynamic plate. The motion heat transfer test system provided by the application is reliable and has replaceable components, and can effectively simulate various test working conditions and heat transfer modes.

Description

Technical Field

[0001] This application relates to the field of spacecraft vacuum thermal testing technology, and in particular to a motion heat transfer testing system and method for spacecraft vacuum thermal testing. Background Technology

[0002] With the development of space technology, the requirements for thermal management systems in spacecraft are becoming increasingly stringent. On-orbit spacecraft, especially those with moving parts, face significant challenges in verifying heat transfer mechanisms and heat dissipation efficiency in high-vacuum environments. Currently, the common heat conduction method for satellites and rockets involves uniformly applying thermal grease to the hot end to maintain a tight connection with a heat pipe. The high thermal conductivity of the heat pipe transfers heat to the satellite / rocket's heat dissipation surface for release. Thermal grease has good fluidity, effectively filling the gap between the hot and cold ends, and its high thermal conductivity allows for the creation of a good heat conduction channel at both ends. Heat pipes, on the other hand, achieve efficient heat transfer based on the phase change and circulating flow of the working fluid. The heat pipe achieves rapid heat transfer through the evaporation, transport, condensation, and reflux processes of the working fluid. Because the working fluid is constantly moving within the heat pipe, the heat pipe itself has good uniformity. Furthermore, because its operation is unaffected by gravity, it can still function normally in microgravity and zero-gravity space environments. Heat pipes themselves have high reliability and stability, and their simple structure requires no additional power drive.

[0003] Thermal design assumes that the cold and hot ends of the heat transfer system are in fixed relative positions and have sufficient preload to fully utilize the cold end's heat dissipation from the hot end. However, when the hot end is not fixed relative to the cold end and relative motion is required, common heat dissipation structure designs cannot achieve effective heat transfer, and there is a lack of experimental data on motion-based heat transfer.

[0004] Therefore, it is necessary to provide a motion heat transfer test system for spacecraft vacuum thermal testing to solve the above-mentioned technical problems. Summary of the Invention

[0005] This application aims to provide a motion heat transfer test system for spacecraft vacuum thermal testing, in order to solve the technical problems in the prior art, such as the inability to effectively simulate or verify the heat dissipation efficiency of moving parts of spacecraft under high vacuum conditions in orbit. The technical problems to be solved by this application are achieved through the following technical solutions.

[0006] The first aspect of this application proposes a motion heat transfer test system for vacuum thermal testing of spacecraft, comprising: a movable plate 5, on which heating elements are attached, the movable plate 5 providing adjustable heat dissipation power to simulate the heat dissipation effect of a product; a stationary plate 6, movably connected to the movable plate 5 and forming a nested protruding structure so that when the movable plate 5 is driven, the movable plate 5 can reciprocate relative to the stationary plate 6; a driving end including a torque sensor 1, a telescopic motor 2, and a connecting push rod 3, the connecting push rod 3 being connected to the movable plate 5 to transmit driving force to drive the movable plate to reciprocate relative to the stationary plate; and a heat dissipation support structure, the heat dissipation support structure including a cold plate bracket 4, a cold plate support column 8, and a liquid nitrogen cold plate 7; wherein, the heat dissipation efficiency of the movable plate 5 is adjusted by controlling and adjusting the motion frequency of the movable plate 5.

[0007] The second aspect of this application proposes a motion heat transfer test method for spacecraft vacuum thermal testing. This method employs the motion heat transfer test system for spacecraft vacuum thermal testing described in the first aspect of this application. The motion heat transfer test method includes: placing the motion heat transfer test system in a vacuum state; pressurizing liquid nitrogen to a specified value; supplying liquid nitrogen to the liquid nitrogen cold plate; waiting for the temperature measuring point on the stationary plate cover to drop and stabilize; applying different powers to the heating element on the moving plate; calculating the thermal conductivity based on the temperature difference between the stationary plate cover and the moving plate; verifying the thermal conductivity under different materials by changing the material of the rolling balls; and verifying the thermal conductivity under different contact areas by changing the number of rolling balls.

[0008] A third aspect of this application provides an electronic device, comprising: one or more processors; a storage device for storing one or more programs; wherein when the one or more programs are executed by the one or more processors, the one or more processors implement the method described in the first aspect of this application.

[0009] A fourth aspect of this application provides a computer-readable medium having a computer program stored thereon, which, when executed by a processor, implements the method described in the first aspect of this application.

[0010] The embodiments of this application have the following advantages:

[0011] Compared with the prior art, this application can flexibly adjust the power of the heating element on the hot end moving plate to simulate different heat dissipation, simulate different material combinations by changing the materials of the hot end moving plate and the cold end stationary plate, simulate different contact gaps and contact forms by configuring the size and protrusion height of the ball bearings, and simulate different thermal interface materials by using the type of thermally conductive filling material and thermally conductive silicone grease. It can effectively simulate various test conditions and heat transfer modes.

[0012] When it is necessary to change the test conditions (such as different materials, different gaps, different balls, etc.), the hot end moving plate can be quickly replaced without extensive disassembly and reassembly of the entire system. This design greatly simplifies the equipment assembly and testing process, significantly shortens the test preparation and cycle, and improves R&D efficiency.

[0013] Furthermore, this application supports the verification of multiple heat transfer methods and has highly configurable characteristics. It can be used to verify various heat transfer methods and approaches, including the interaction of contact thermal resistance, radiation heat transfer, and frictional heat generation in a dynamic vacuum environment, thereby providing an effective solution for the thermal management of space mechanisms.

[0014] Furthermore, this application is easy to operate, has good repeatability, and integrates a torque sensor, a telescopic motor, and a precise measurement and control unit, ensuring automation and precise control of the testing process. The motor-driven reciprocating motion has good repeatability, making the results of multiple tests comparable and ensuring the reliability of the data. Attached Figure Description

[0015] Figure 1 This is a schematic structural diagram of the motion heat transfer test system for spacecraft vacuum thermal testing according to this application;

[0016] Figure 2 This is a partial structural schematic diagram of the moving plate, stationary plate, and heat dissipation support mechanism in the motion heat transfer test system for spacecraft vacuum thermal testing according to this application;

[0017] Figure 3 This is a partial structural schematic diagram of the stationary plate in the motion heat transfer test system for spacecraft vacuum thermal testing according to this application;

[0018] Figure 4 This is a partial three-dimensional structural diagram of the moving plate and stationary plate in the motion heat transfer test system for vacuum thermal testing of spacecraft, as described in this application.

[0019] Figure 5 This is a schematic flowchart of the motion heat transfer test method for spacecraft vacuum thermal testing according to this application;

[0020] Figure 6 This is a schematic diagram of the structure of an electronic device embodiment according to this application;

[0021] Figure 7 This is a schematic diagram of a computer-readable medium embodiment according to the present application. Detailed Implementation

[0022] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0023] In view of the above problems, this application proposes a motion heat transfer test system for spacecraft vacuum thermal testing. The motion heat transfer test system includes: a movable plate with a heating element attached, the movable plate providing adjustable heat dissipation power to simulate the heat dissipation effect of the product; a stationary plate movably connected to the movable plate, allowing the movable plate to reciprocate relative to the stationary plate when driven; and a drive end including a torque sensor, a telescopic motor, and a connecting push rod, the drive end driving the movable plate to reciprocate relative to the stationary plate. The heat dissipation efficiency is increased by controlling and adjusting the movement frequency of the movable plate. By driving the movable plate and stationary plate relative to each other via the telescopic motor, the system simulates sliding friction heat transfer between a hot end with adjustable heat dissipation power and different hot and cold end materials, different contact forms, and different heat transfer filling materials. The temperature change of the hot end is recorded, thereby calculating the heat transfer efficiency. This provides basic experimental data for the design of a movable heat transfer platform and can also serve as experimental basis for spacecraft thermal analysis and thermal design under different motion conditions.

[0024] It should be noted that the system of this application has a wide range of applications, and is particularly suitable for the motion heat transfer verification method of spacecraft vacuum thermal test. It has a flexible structure and is easy to operate. By changing the heat dissipation power on the moving plate, the material of the moving plate and the stationary plate, and the thermally conductive filler, the heat exchange mode under different motion states can be simulated, and a large amount of motion heat transfer test data can be obtained for the study of the motion heat transfer mechanism of spacecraft and design verification.

[0025] Example 1

[0026] The following reference Figures 1 to 4 The contents of this application will be described in detail.

[0027] Figure 1 This is a schematic structural diagram of the motion heat transfer test system for spacecraft vacuum thermal testing according to this application.

[0028] Reference Figures 1 to 3 The motion heat transfer testing system includes: a moving plate 5, with heating elements attached, which provides adjustable heat dissipation power to simulate the heat dissipation effect of a product; a stationary plate 6, movably connected to the moving plate 5 and forming a nested protruding structure so that the moving plate 5 can reciprocate relative to the stationary plate 6 when the moving plate 5 is driven; a driving end, including a torque sensor 1, a telescopic motor 2, and a connecting push rod 3, which drives the moving plate 5 (e.g., the hot-end moving plate) to reciprocate relative to the stationary plate 6 (e.g., the cold-end stationary plate); and a heat dissipation support structure, which includes a cold plate bracket 4, a cold plate support column 8, and a liquid nitrogen cold plate 7. The moving plate 5 is connected to the connecting push rod 3. The heat dissipation efficiency is increased by controlling and adjusting the movement frequency of the moving plate 5.

[0029] See Figure 1 and Figure 2 The driving end includes a torque sensor 1, a telescopic motor 2, and a connecting push rod 3. The driving end is used to drive the moving plate 5 to reciprocate relative to the stationary plate 6. Specifically, the moving plate 5 reciprocates on the stationary plate 6.

[0030] Specifically, the torque sensor 1 is mounted on the base plate using four M6 screws via a dedicated mounting base. The base plate has elongated holes for adjusting the mounting position according to the transfer distance.

[0031] Torque sensor 1 and telescopic motor 2 are connected by matching connectors, which are tightened and fixed by, for example, M5 screws. Telescopic motor 2 has a margin of movement in the vertical direction, which is limited by subsequent installation.

[0032] It should be noted that in this application, the vertical direction is defined as the up-down direction of the attached drawing paper, and the horizontal direction is defined as the left-right direction of the attached drawing paper that is perpendicular to the vertical direction.

[0033] Furthermore, the telescopic motor 2 is connected to the adapter push rod 3 using two M5 screws via a connector. Due to the limitation of the adapter push rod base, the telescopic motor can be fixed to a preset position using the vertical movement allowance, and the telescopic motor 2 is suspended to the position to be activated. The right end of the adapter push rod 3 is connected to the moving plate 5 via an M5 thread.

[0034] In one specific embodiment, the telescopic motor 2 is a programmable motor, the moving plate 5 is the hot-end moving plate, and the stationary plate 6 is the cold-end stationary plate. A motor-driven control mode is adopted to achieve reciprocating motion of the moving plate 5 relative to the stationary plate 6 within a range of ±40mm, with an interval of 100ms and a speed of 100mm / s. The motion range (maximum ±100mm), interval time (minimum 50ms), and speed (maximum 150mm / s) can be modified via software to meet the needs of different simulations.

[0035] Specifically, the movable plate 5 is mounted on the stationary plate 6 and is movable relative to the stationary plate 6. The movable plate 5 is made of aluminum alloy, for example, using aluminum alloy with good thermal conductivity, and its dimensions are, for example, 300mm × 200mm. Aluminum alloy has good thermal conductivity, which can effectively simulate the self-heating of components, frictional heat generation, and scenarios under different thermal conduction conditions. It simulates the heat dissipation conditions of rapidly moving, high-heat-generating components, providing data and experimental support for the thermal control design of subsystems and the entire satellite.

[0036] like Figure 2As shown, the moving plate 5 is in direct contact with the ball bearings 11 (brass ball bearings in this example) to simulate the contact environment of dynamic heat transfer. For example, fifty ball bearings 11 are located in the corresponding grooves of the stationary plate 6, and their positions are restricted by the stationary plate cover 10 to prevent them from falling out. The upper surface of the stationary plate cover 10 and the lower surface of the moving plate 5 have a gap (e.g., 1 mm). The ball bearings 11 serve as supports, and molybdenum disulfide is sprayed onto the contact surfaces of the ball bearings 11 with both the moving plate 5 and the stationary plate 6 for solid lubrication. In addition, the lower part of the stationary plate 6 is connected and pressed tightly to the liquid nitrogen cooling plate 7 by four M8 screws, and low-temperature thermal grease is applied between the two to ensure good heat exchange.

[0037] Specifically, the liquid nitrogen cold plate 7 is embedded in the cold plate bracket 4 and is positioned using four M6 set screws. Cold plate supports 8 are inserted into the four mounting holes of the cold plate bracket 4, and the cold plate bracket 4 and cold plate supports 8 are thermally insulated together using polyimide insulation columns. The top of the cold plate supports 8 is fixed to the base plate using M8 threads. After the mechanical parts are installed, temperature measuring points are installed in the corresponding grooves of the stationary plate cover 10, using, for example, a 0.2mm diameter thermocouple as the temperature measuring point.

[0038] Furthermore, a heating element is provided on the upper surface of the moving plate 5, and the power of the heating element is, for example, 30W. The heating element is used to simulate the internal heat dissipation of spacecraft components. Specifically, the heating power is adjusted by changing the current of the heating element to adapt to the test requirements under different heat dissipation conditions. By precisely controlling the power of the heating element, the heat dissipation conditions of, for example, high-power moving spaceborne equipment can be simulated.

[0039] For example, a 45×55mm heating element with a maximum power of 25W is attached to the moving plate 5 as a heat source. Three temperature observation points are evenly arranged from the center of the heat source to the edge of the moving plate 5 for connecting and measuring the temperature.

[0040] Threaded holes are provided on both sides of the moving plate 5 for mounting counterweight units. The counterweight units can simulate the thermal conductivity under different preload conditions by using gravity with different weights of counterweights. The preload is an important parameter in the final assembly of the product and directly affects the contact state between the product and the heat dissipation surface.

[0041] Furthermore, temperature-measuring thermocouples are evenly distributed on the moving plate 5, arranged around the heating element, and are attached to the moving plate 5 by adhesive. These thermocouples are used to monitor the temperature changes of the moving plate 5 in real time and at multiple points during movement and heating. The temperature data fed back by these thermocouples can reflect the thermal conductivity efficiency of the system and the heat distribution on the moving plate 5 under current operating conditions, and provide data basis for whether the system has entered a thermally stable state.

[0042] like Figure 2As shown, the stationary plate 6 is mounted on the liquid nitrogen cold plate 7 of the heat dissipation support structure. Further, the cold plate bracket 4 is mounted on the cold plate support column 8. The liquid nitrogen cold plate 7 is mounted on the cold plate bracket 4. For example, the stationary plate 6 is fastened to the liquid nitrogen cold plate 7 with four M6 screws. Thermal grease is applied between the stationary plate 6 and the liquid nitrogen cold plate 7 to minimize contact thermal resistance, enhance heat conduction efficiency, and ensure that the cooling capacity of the liquid nitrogen cold plate is effectively transferred to the stationary plate 6.

[0043] Optionally, the stationary plate 6 is made of aluminum alloy, specifically aluminum alloy material, with dimensions such as 350mm×250mm. As the cold end of the motion heat transfer test, the stationary plate 6 is responsible for receiving the heat from the moving plate 5 and transferring it to the liquid nitrogen cold plate for heat dissipation. In addition to aluminum alloy, other metal materials with good thermal conductivity can be used as alternative materials for the stationary plate 6.

[0044] Preferably, thermally conductive silicone grease is applied between the stationary plate 6 and the liquid nitrogen cold plate 7.

[0045] from Figure 3 As can be seen from the diagram, the stationary plate 6 includes a stationary plate base 9, ball bearings 11, and a stationary plate cover 10. The stationary plate base 9 serves as the main body of the stationary plate 6. A plurality of ball bearings 11 are embedded in the stationary plate base 9. A portion of each ball bearing 11 protrudes from the upper surface of the stationary plate base 9, meaning a portion of the ball bearing 11 is embedded within the stationary plate base 9. A portion of the ball bearing 11 protrudes from the upper surface of the stationary plate base 9 and has a first protrusion height. In other words, the upper surface of the ball bearing 11 is closer to the outer side than the upper surface of the stationary plate base 9. By changing the size of the ball bearings (11), the first protrusion height is within the range of 1 mm to 3 mm.

[0046] Furthermore, the ball bearing 11 is fitted into the corresponding sleeve hole of the stationary plate cover 10, and protrudes from the upper surface of the stationary plate cover 10, having a second protrusion height (corresponding to...). Figure 3 The ball bearing 11, the stationary plate base 9, and the stationary plate cover 10 form a nested protruding structure, wherein the height of the second protrusion is in the range of 0.5mm to 2mm, thereby enabling the stationary plate base 9 and the stationary plate cover 10 to form an adjustable gap.

[0047] By protruding from the static plate base, the gaps and point or line contact heat transfer modes between moving parts of a spacecraft can be accurately simulated. Specifically, through the geometry of the ball bearings and the height of the protrusion, the contact surface is in a state of minute gaps, which can more effectively simulate the contact thermal resistance and microscopic heat transfer mechanism caused by gaps in a vacuum environment. This allows for more effective verification of heat transfer effects under different test conditions, thereby improving the reliability of the simulation test.

[0048] In this example, ball 11 is made of brass, there are 50 balls of H62 material, and the diameter of the ball is 5mm. Ball array center groove: A 1.5mm × 1.5mm groove is cut in the center of the ball array for placing thermocouples, enabling local temperature monitoring inside the ball array and further refining the analysis of the contact heat transfer process.

[0049] The stationary plate cover 10 is fixed to the stationary plate base 9 by, for example, four M3 screws, to confine the ball bearing 11 between the stationary plate cover 10 and the stationary plate base 9, thereby preventing it from falling off. The surface of the stationary plate cover 10 is lubricated with molybdenum disulfide spraying, ensuring that the ball bearing 11 can roll smoothly when the moving plate 5 slides above the stationary plate 6, reducing additional frictional resistance, and further ensuring the authenticity and reliability of the simulation test.

[0050] The static plate 6 features a replaceable modular design. By changing the material of the static plate 6 (such as alloys with different thermal conductivity), modules can be replaced to change the size, shape, and arrangement of the balls, as well as the simulated contact gap. This allows for flexible verification of heat transfer effects under different test conditions, greatly shortening the test cycle.

[0051] Furthermore, the inlet and outlet of the liquid nitrogen cooling plate 7 both adopt a 10mm diameter blade interface design, with evenly distributed liquid nitrogen flow channels inside. It employs friction stir welding and is fixed to the cooling plate bracket 4 on the side using four M6 screws. The surface of the liquid nitrogen cooling plate 7 is arranged in a matrix with a 60mm spacing (e.g., four rows and five columns, i.e., 4×5). The stationary plate 6 is installed on the liquid nitrogen cooling plate 7 through twenty M6 threaded mounting holes. Except for the area covered by the moving plate 5, the remaining exposed parts are covered with multiple layers. The liquid nitrogen cooling plate 7 uses, for example, 30mm×30mm angle steel and has four external support ears. Polyimide is used for insulation between the support ears and the support column. The distance between the cooling plate and the mounting base plate is greater than 70mm to prevent contact leakage and ensure the temperature of the liquid nitrogen cooling plate 7 is maintained.

[0052] In one specific embodiment, the drive end is powered by the telescopic motor 2. The motor frequency is set according to the contact frequency required for dynamic heat transfer. The correctness of the output torque is determined by the torque sensor 1. After the test parameters are determined, the torque sensor 1, the telescopic motor 2, and the adapter push rod 3 are installed on the test platform and adjusted to be horizontal and coaxial.

[0053] Next, the cold plate support column 8, cold plate bracket 4, and liquid nitrogen cold plate 7 are assembled together to form the cooling source of the cold end stationary plate. The cold plate base 9 is installed on the liquid nitrogen cold plate 7, and ball bearings 11 are installed on the cold plate base 9. Molybdenum disulfide is evenly applied between the ball bearings 11 and the stationary plate base 9 for lubrication, and then the stationary plate cover is covered to prevent the ball bearings 11 from falling off. Thus, the cold end heat dissipation part is completed. Different types and specifications of heat-conducting materials are added between the cold plate base 9 and the liquid nitrogen cold plate 7 according to different test requirements for heat exchange.

[0054] The movable plate 5, with adjustable heat dissipation power, is connected to the adapter push rod 3. A 30W heating element is attached to the movable plate 5, and the heating element is connected to the power supply via a heating cable. Simultaneously, counterweight units of appropriate weight are installed in the threaded holes on both sides of the movable plate 5 to simulate the contact effect between the actual product and the stationary plate. Temperature-measuring thermocouples are evenly distributed and attached to the movable plate 5 to record the heat changes on the movable plate 5 in real time.

[0055] After all components are assembled, the motor control unit and controller are connected to the computer control software. The motion frequency of the telescopic motor 2 is set according to the test requirements to simulate the actual motion trajectory of the product. After the telescopic motor 2 is started, the moving plate 5 slides horizontally according to the specified parameters, indicating that the motion heat transfer test system is working normally.

[0056] Furthermore, a simulation test was conducted using the aforementioned motion heat transfer test system. First, a liquid nitrogen Dewar was used to cool the liquid nitrogen cold plate 7 through a liquid nitrogen pipeline. Temperature measuring thermocouples were evenly distributed on the liquid nitrogen cold plate 7. Once the temperature dropped to the standard requirements, it was ready for use.

[0057] The test container was evacuated, and liquid nitrogen was pressurized to 0.05 MPa. Liquid nitrogen was supplied to the cold plate 7. After the temperature measuring point on the stationary plate cover 10 dropped and stabilized, different powers were applied to the heating element on the moving plate 5. The thermal conductivity was calculated by the temperature difference between the stationary plate cover 10 and the moving plate 5.

[0058] Start the heating unit on the moving plate 5 to provide the heat consumption power required for the test, and record the data after the temperature measurement point on the moving plate 5 rises to the equilibrium temperature.

[0059] Place the moving plate 5 on the stationary plate 6, then start the drive control program of the telescopic motor 2, edit the required number of movements and time, and drive the telescopic motor 2 according to the system programming to make the moving plate 5 move back and forth uniformly on the stationary plate 6 at the given speed. Record the temperature drop on the moving plate 5 at different time intervals to analyze the heat transfer effect.

[0060] By using this motion heat transfer testing system, the power of the heating element on the moving plate 5 can be adjusted to simulate the actual heat dissipation of the product. The movement frequency of the moving plate 5 can also be adjusted to increase heat dissipation efficiency. The specific heat transfer effect of the stationary plate 6 can be verified by adjusting the material of the stationary plate 6, the size of the ball bearings 11, the type of thermally conductive filling material, and the type of thermal grease.

[0061] Optionally, by achieving a vacuum degree of 1×10 -2The thermal conductivity was measured under low convective heat conduction conditions (Pa), reducing the influence of convection on the thermal conductivity measurement. By specifying different reciprocating step lengths and frequencies for the telescopic motor 2, and using 0.2mm thermocouple wire with low heat capacity, the error caused by the heat capacity at the temperature measurement point can be effectively reduced when calculating thermal conductivity. The size of the simulated heat source can be changed by adjusting the size of the heating element attached to the moving plate 5 and the applied power. By changing the material of the ball bearings 11 (e.g., brass, copper, aluminum alloy, etc.), the thermal conductivity under different materials can be effectively verified, and by changing the number, the thermal conductivity under different contact areas can be verified. The contact area is adjusted by adjusting the size of the stationary plate 6 and the number of ball bearing grooves.

[0062] By adjusting the stationary plate 6 to a liquid nitrogen temperature (approximately -195°C) and maintaining its stability, the error in thermal conductivity calculation was reduced. The force required for the displacement of the moving plate 5 was measured under different temperatures and thermal conductivity conditions, with a measurement cycle of 10 ms. The magnitude of the prestress during movement can be changed by adjusting the counterweight on the moving plate 5. The system of this application has long-term operating capability, with a trouble-free operating time exceeding 100 hours.

[0063] In one specific implementation, a task requires the heat-consuming component to move rapidly within a specified rectangular area to verify the optimal heat transfer structure under various contact modes, ensuring that the temperature of the high heat-consuming product remains within the operating temperature range. Each movement step is 40mm, the speed is 100mm / s, and the simulated heat consumption is set at 15W. The results to be measured are the thermal conductivity of the system, the force required for movement under different filling states, and the heat distribution on the moving plate 5.

[0064] When the test begins, the stationary plate 6 is sprayed with molybdenum disulfide and filled with fifty ball bearings 11. The stationary plate cover plate 9 is installed, and the stationary plate base 9 is coated with thermal grease and then installed on the liquid nitrogen cold plate 7. Thermocouples are attached to special grooves on the stationary plate cover plate 10 to monitor the thermal conductivity between the liquid nitrogen cold plate 7 and the stationary plate 6 and to serve as the boundary temperature for heat transfer. After the stationary plate 6 is installed, the liquid nitrogen cold plate 7 is covered with, for example, a multi-layer thermal insulation component of ten units to prevent heat from affecting the moving plate 5 through radiation. Finally, the liquid nitrogen cold plate 7 is installed on a universal base plate through the cold plate bracket 4 and the cold plate support 8.

[0065] Specifically, the side of the moving plate 5 that contacts the stationary plate 6 is the inner surface, and the side of the moving plate 5 opposite to the inner surface is the outer surface. A heating element is attached to the center of the outer surface of the moving plate 5, and the surface area of ​​the heating element is greater than or equal to 15 cm². 2 This meets the heating requirements. Four thermocouples are evenly distributed along a straight line on the moving plate 5 to monitor the temperature distribution. The outer surface of the moving plate 5 is covered with, for example, a multi-layer heat insulation component with ten units to prevent radiative heat dissipation from affecting the test results.

[0066] Connect the moving plate 6 to the adapter push rod 3, then connect it to the telescopic motor 2, and finally install the torque sensor 1 and the telescopic motor 2. Then install the connected components on the universal base plate to assemble the test system.

[0067] The assembled test system is pushed into the vacuum container, and torque sensor 1 and telescopic motor 2 are connected to control and monitor the cable. The inlet and outlet liquid nitrogen pipelines of liquid nitrogen cooling plate 7 are connected, and the thermocouple temperature measuring plug is further connected. The vacuum container door is closed, and the vacuum container is evacuated until the vacuum level inside the vacuum container is less than or equal to 1×10⁻⁶. -2 Pa indicates that the vacuum environment has been established.

[0068] Liquid nitrogen is added to the liquid nitrogen cooling plate 7 and kept flowing. The supply pressure is controlled at 0.05 MPa. After the liquid nitrogen flows through the liquid nitrogen cooling plate 7, it is vented. The temperature is kept decreasing until it stabilizes between -190℃ and -180℃.

[0069] For example, the telescopic motor 2 is set to a speed of 100 mm / s and a step size of 40 mm. When it begins to move, the heating element is powered on at a fixed power of 15W, and temperature changes are observed. When the temperature at all temperature measuring points on the moving plate 5 and the center temperature measuring point on the stationary plate 6 meets the condition that the change rate is less than 0.1℃ / h for four consecutive hours or the monotonic change is less than 0.5℃ for four hours, the temperature is recorded, and the thermal conductivity is calculated. The maximum and minimum values ​​collected by the torque sensor are also recorded to obtain the test results for that experiment. Examples include temperature data and torque data. Further calculations and comparisons are then used to obtain the thermal conductivity, push-pull force, etc.

[0070] In one application example Figure 4 This illustrates a typical motion heat transfer test system, where the test is conducted within a vacuum thermal testing facility (e.g., a vacuum chamber) with a vacuum level requirement better than 1×10⁻⁶. -2Pa, the motor controller and sensor controller in the test system, are connected to the measurement and control computer (e.g., via communication cable) after passing through the vacuum container using a vacuum cable (e.g., a vacuum through-wall cable) and a special flange, enabling closed-loop control of the stroke. The main measurement and control parameters include the parameters set for the telescopic motor 2 of the motion heat transfer test system and the data collected by the torque sensor 1. Thermocouples are temperature-collected using a digital automatic multimeter. Thermocouples inside the vacuum container are measured using a common wire and reference point. Thermocouple temperatures are collected by the digital multimeter via a special vacuum cable and flange, and the data is stored on the test computer for temperature stability assessment and post-test data analysis. Furthermore, the automated liquid nitrogen Dewar is connected to a vacuum flange with an insulated structure via a bellows, and then to a liquid nitrogen cold plate 7 inside the vacuum container via the bellows. Liquid nitrogen is supplied through the liquid nitrogen pipeline, and the interface is sealed with a metal seal to ensure vacuum. The liquid nitrogen passing through the liquid nitrogen cold plate 7 is led out of the vacuum container in the same manner via the bellows and discharged through the flange interface. The simulated heat source attached to the moving plate 5 is implemented using a thin-film heater made of polyimide material. The power supply is connected to the power source outside the vacuum container via a vacuum cable and flange. The power of the heater is controlled by adjusting the power output.

[0071] It should be noted that the above is only an optional example and should not be construed as a limitation of this application.

[0072] Furthermore, the accompanying drawings are merely illustrative of the processes included in the method according to exemplary embodiments of this application and are not intended to be limiting. It is readily understood that the processes shown in the drawings do not indicate or limit the temporal order of these processes. Additionally, it is readily understood that these processes may be executed synchronously or asynchronously, for example, in multiple modules.

[0073] Compared with the prior art, this application can flexibly adjust the power of the heating element on the hot end moving plate to simulate different heat dissipation, simulate different material combinations by changing the materials of the hot end moving plate and the cold end stationary plate, simulate different contact gaps and contact forms by configuring the size and protrusion height of the ball bearings, and simulate different thermal interface materials by using the type of thermally conductive filling material and thermally conductive silicone grease. It can effectively simulate various test conditions and heat transfer modes.

[0074] When it is necessary to change the test conditions (such as different materials, different gaps, different balls, etc.), the hot end moving plate can be quickly replaced without extensive disassembly and reassembly of the entire system. This design greatly simplifies the equipment assembly and testing process, significantly shortens the test preparation and cycle, and improves R&D efficiency.

[0075] Furthermore, this application supports the verification of multiple heat transfer methods and has highly configurable characteristics. It can be used to verify various heat transfer methods and approaches, including the interaction of contact thermal resistance, radiation heat transfer, and frictional heat generation in a dynamic vacuum environment, thereby providing an effective solution for the thermal management of space mechanisms.

[0076] Furthermore, this application is easy to operate, has good repeatability, and integrates a torque sensor, a telescopic motor, and a precise measurement and control unit, ensuring automation and precise control of the testing process. The motor-driven reciprocating motion has good repeatability, making the results of multiple tests comparable and ensuring the reliability of the data.

[0077] Example 2

[0078] The following are embodiments of the method of this application, which can be used to perform motion heat transfer experiments using the system embodiments of this application. For details not disclosed in the method embodiments of this application, please refer to the system embodiments of this application.

[0079] Figure 5 This is the schematic diagram of the motion heat transfer test method for vacuum thermal testing of spacecraft proposed in this application.

[0080] Reference Figure 5 The second aspect of this disclosure provides a motion heat transfer test method for spacecraft vacuum thermal testing, which uses the motion heat transfer test system for spacecraft vacuum thermal testing described in the first aspect of this application to conduct the motion heat transfer test.

[0081] The method for testing heat transfer in motion includes the following steps.

[0082] Step S101: Place the motion heat transfer test system in a vacuum state, pressurize the liquid nitrogen to a specified value, supply liquid nitrogen to the liquid nitrogen cold plate, wait for the temperature measuring point on the stationary plate cover 10 to drop and stabilize, apply different powers to the heating plate on the moving plate, and calculate the thermal conductivity by the temperature difference between the stationary plate cover 10 and the moving plate 5.

[0083] Step S102: By changing the material of the ball 11, the thermal conductivity under different materials is verified. By changing the number of balls, the thermal conductivity under different contact areas is verified.

[0084] In one specific embodiment, the assembled test system is pushed into the vacuum container, and the torque sensor 1 and the telescopic motor 2 are connected to control the monitoring cable. The inlet and outlet liquid nitrogen pipelines of the liquid nitrogen cooling plate 7 are connected, and the thermocouple temperature measuring plug is further connected. The vacuum container door is closed, and the vacuum container is evacuated until the vacuum level inside the vacuum container is less than or equal to 1×10⁻⁶. -2 Pa indicates that the vacuum environment has been established.

[0085] Liquid nitrogen is added to the liquid nitrogen cooling plate 7 and kept flowing. The supply pressure is controlled at 0.05 MPa. After the liquid nitrogen flows through the liquid nitrogen cooling plate 7, it is vented. The temperature is kept decreasing until it stabilizes between -190℃ and -180℃.

[0086] The telescopic motor 2 is a stepper motor. It is used in conjunction with a control drive to enable the moving plate 5 to reciprocate within a 40mm range relative to the stationary plate 6. The telescopic motor 2 is set to a speed of 100mm / s and a step size of 40mm. Once movement begins, the heating element is powered at a fixed power of 15W, and temperature changes are observed. When the temperature at all temperature measuring points on the moving plate 5 and the center temperature measuring point on the stationary plate 6 meets the requirement that the change rate is less than 0.1℃ / h for four consecutive hours or the monotonic change is less than 0.5℃ for four hours, the temperature is recorded, and the thermal conductivity is calculated. The maximum and minimum values ​​collected by the torque sensor are also recorded to obtain the experimental results.

[0087] Threaded holes are provided on both sides of the moving plate 5 for mounting counterweight units. These counterweight units can be used to adjust and control the contact pressure between the moving plate 5 and the stationary plate 6 to simulate the contact loads of different spacecraft components, for example, a maximum contact load of 10 kg. Heating elements are attached to the upper surface of the moving plate 5 to simulate internal heat loss of spacecraft components or external heat flow such as solar radiation. Temperature-measuring thermocouples are evenly distributed around the heating elements. The moving plate 5 and the stationary plate 6 are both made of aluminum alloy, and the ball bearings 11 are made of brass.

[0088] Furthermore, the stationary plate 6 includes a stationary plate base 9, ball bearings 11, and a stationary plate cover 10. The stationary plate base 9 serves as the main body of the stationary plate 6, and a plurality of ball bearings 11 are embedded in the stationary plate base 9. A portion of the ball bearing 11 is embedded in the stationary plate base 9, and a portion of the ball bearing 11 protrudes from the upper end face of the stationary plate base 9 and has a first protrusion height, which is between 1 mm and 3 mm. The ball bearing 11 is fitted into the corresponding sleeve hole of the stationary plate cover 10 and protrudes from the upper surface of the stationary plate cover 10 and has a second protrusion height. The ball bearing 11, the stationary plate base 9, and the stationary plate cover 10 form a nested protrusion structure, wherein the second protrusion height is between 0.5 mm and 2 mm.

[0089] Optionally, by removing the stationary plate 6 of the motion heat transfer test system, changing the diameter or number of the balls 11, a new stationary plate base 10 is made, the stationary plate cover 10 is re-sprayed with molybdenum disulfide, the thermocouple measuring point in the center of the stationary plate is re-attached, and thermal grease is applied to the lower surface of the remade stationary plate 6 for mounting on the liquid nitrogen cold plate 7. Thermal grease is applied in the gap between the stationary plate 6 and the moving plate 5, and a counterweight is installed on the moving plate 5 to maintain good contact. The test is then started, and the relevant test data are recorded.

[0090] It should be noted that the system used in the method of this application is the same as the system in Embodiment 1, therefore, the description of the same parts has been omitted.

[0091] Compared with the prior art, this application can flexibly adjust the power of the heating element on the hot end moving plate to simulate different heat dissipation, simulate different material combinations by changing the materials of the hot end moving plate and the cold end stationary plate, simulate different contact gaps and contact forms by configuring the size and protrusion height of the ball bearings, and simulate different thermal interface materials by using the type of thermally conductive filling material and thermally conductive silicone grease. It can effectively simulate various test conditions and heat transfer modes.

[0092] When it is necessary to change the test conditions (such as different materials, different gaps, different balls, etc.), the hot end moving plate can be quickly replaced without extensive disassembly and reassembly of the entire system. This design greatly simplifies the equipment assembly and testing process, significantly shortens the test preparation and cycle, and improves R&D efficiency.

[0093] Furthermore, this application supports the verification of multiple heat transfer methods and has highly configurable characteristics. It can be used to verify various heat transfer methods and approaches, including the interaction of contact thermal resistance, radiation heat transfer, and frictional heat generation in a dynamic vacuum environment, thereby providing an effective solution for the thermal management of space mechanisms.

[0094] Furthermore, this application is easy to operate, has good repeatability, and integrates a torque sensor, a telescopic motor, and a precise measurement and control unit, ensuring automation and precise control of the testing process. The motor-driven reciprocating motion has good repeatability, making the results of multiple tests comparable and ensuring the reliability of the data.

[0095] Figure 6 This is a schematic diagram of the structure of an electronic device embodiment according to this application.

[0096] like Figure 6 As shown, the electronic device is presented in the form of a general-purpose computing device. There can be one or multiple processors working collaboratively. This application also does not exclude distributed processing, meaning that processors can be distributed across different physical devices. The electronic device of this application is not limited to a single entity, but can also be the sum of multiple physical devices.

[0097] The memory stores a computer-executable program, typically machine-readable code. The computer-readable program can be executed by the processor to enable the electronic device to perform the methods of this application, or at least some steps of those methods.

[0098] The memory includes volatile memory, such as random access memory (RAM) and / or cache memory, and may also be non-volatile memory, such as read-only memory (ROM).

[0099] Optionally, in this embodiment, the electronic device further includes an I / O interface for exchanging data with external devices. The I / O interface can represent one or more of several bus structures, including a memory cell bus or memory cell controller, a peripheral bus, a graphics acceleration port, a processing unit, or a local bus using any of the various bus structures.

[0100] It should be understood that Figure 6 The electronic device shown is merely an example of this application, and the electronic device of this application may also include elements or components not shown in the above examples. For example, some electronic devices also include display units such as displays, and some electronic devices also include human-computer interaction elements such as buttons and keyboards. As long as the electronic device can execute a computer-readable program in memory to implement the method or at least part of the steps of the method of this application, it can be considered as an electronic device covered by this application.

[0101] From the above description of the embodiments, those skilled in the art will readily understand that the exemplary embodiments described herein can be implemented by software, or by combining software with necessary hardware. Therefore, as... Figure 7 As shown, the technical solution according to the embodiments of this application can be embodied in the form of a software product. The software product can be stored in a non-volatile storage medium (such as a CD-ROM, USB flash drive, mobile hard drive, etc.) or on a network, and includes several commands to cause a computing device (such as a personal computer, server, or network device, etc.) to execute the above-described method according to the embodiments of this application.

[0102] The software product may employ any combination of one or more readable media. A readable medium may be a readable signal medium or a readable storage medium. A readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of readable storage media (a non-exhaustive list) include: electrical connections with one or more wires, portable disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fibers, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof.

[0103] The computer-readable storage medium may include data signals propagated in baseband or as part of a carrier wave, carrying readable program code. Such propagated data signals may take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. The readable storage medium may also be any readable medium other than a readable storage medium, capable of transmitting, propagating, or transmitting programs for use by or in connection with a command execution system, apparatus, or device. The program code contained on the readable storage medium may be transmitted using any suitable medium, including but not limited to wireless, wired, optical fiber, RF, etc., or any suitable combination thereof.

[0104] Program code for performing the operations of this application can be written in any combination of one or more programming languages, including object-oriented programming languages ​​such as Java and C++, and conventional procedural programming languages ​​such as C or similar languages. The program code can execute entirely on the user's computing device, partially on the user's device, as a standalone software package, partially on the user's computing device and partially on a remote computing device, or entirely on a remote computing device or server. In cases involving remote computing devices, the remote computing device can be connected to the user's computing device via any type of network, including a local area network (LAN) or a wide area network (WAN), or it can be connected to an external computing device (e.g., via the Internet using an Internet service provider).

[0105] The aforementioned computer-readable medium carries one or more programs (e.g., computer-executable programs) that, when executed by a device, cause the computer-readable medium to implement the methods of this disclosure.

[0106] Those skilled in the art will understand that the above modules can be distributed in the device as described in the embodiments, or they can be modified accordingly and placed in one or more devices that are unique to this embodiment. The modules in the above embodiments can be combined into one module, or they can be further divided into multiple sub-modules.

[0107] Through the description of the above embodiments, those skilled in the art will readily understand that the exemplary embodiments described herein can be implemented by software or by combining software with necessary hardware. Therefore, the technical solutions according to the embodiments of this application can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (such as a CD-ROM, USB flash drive, external hard drive, etc.) or on a network, including several commands to cause a computing device (such as a personal computer, server, mobile terminal, or network device, etc.) to execute the methods according to the embodiments of this application.

[0108] Exemplary embodiments of this application have been specifically shown and described above. It should be understood that this application is not limited to the detailed structures, arrangements, or implementation methods described herein; rather, this application is intended to cover various modifications and equivalent arrangements contained within the spirit and scope of the appended claims.

Claims

1. A motion heat transfer test system for vacuum thermal testing of spacecraft, characterized in that, include: The movable plate (5) is equipped with heating elements. The movable plate (5) is used to provide adjustable heat dissipation power to simulate the heat dissipation effect of the product. The stationary plate (6) is movably connected to the moving plate (5) and has a nested protruding structure so that when the moving plate (5) is driven, the moving plate (5) can reciprocate relative to the stationary plate (6); The driving end includes a torque sensor (1), a telescopic motor (2), and a transfer push rod (3). The transfer push rod (3) is connected to the moving plate (5) to transmit driving force to drive the moving plate (5) to reciprocate relative to the stationary plate (6). as well as The heat dissipation support structure includes a cold plate bracket (4), a cold plate support column (8), and a liquid nitrogen cold plate (7); wherein, The heat dissipation efficiency of the moving plate (5) can be adjusted by controlling and adjusting the movement frequency of the moving plate (5); Threaded holes are provided on both sides of the moving plate (5) for installing counterweight units. The counterweight units are used to adjust and control the contact pressure between the moving plate (5) and the stationary plate (6) to simulate the contact load of different spacecraft components. The stationary plate (6) includes a stationary plate base (9), ball bearings (11) and a stationary plate cover (10). The stationary plate base (9) serves as the main body of the stationary plate (6), and multiple ball bearings (11) are inlaid on the stationary plate base (9). A portion of the ball (11) is embedded in the static plate base (9), and a portion of the ball (11) protrudes from the upper end face of the static plate base (9) and has a first protrusion height, which is between 1 mm and 3 mm. The ball (11) is fitted into the corresponding hole of the stationary plate cover (10) and protrudes from the upper surface of the stationary plate cover (10) with a second protrusion height. The ball (11), the stationary plate base (9), and the stationary plate cover (10) form a nested protrusion structure, wherein the second protrusion height is between 0.5 mm and 2 mm.

2. The motion heat transfer test system according to claim 1, characterized in that, include: The telescopic motor (2) is a stepper motor. The telescopic motor (2) is used in conjunction with the control drive to make the moving plate (5) reciprocate within 40mm relative to the stationary plate (6).

3. The motion heat transfer test system according to claim 1, characterized in that, include: A heating element is attached to the upper surface of the moving plate (5) to simulate the internal heat loss of spacecraft components or the external heat flow from solar radiation. Temperature measuring thermocouples are evenly distributed around the heating element.

4. The motion heat transfer test system according to claim 1, characterized in that, include: The moving plate (5) is made of aluminum alloy, the stationary plate (6) is made of aluminum alloy, and the ball bearings (11) are made of brass.

5. A method for testing the heat transfer of motion in a spacecraft vacuum thermal test, characterized in that, It employs the motion heat transfer test system for spacecraft vacuum thermal testing as described in any one of claims 1 to 4 to conduct motion heat transfer tests, wherein the motion heat transfer test method includes: The motion heat transfer test system is placed in a vacuum state, liquid nitrogen is pressurized to a specified value, liquid nitrogen is supplied to the liquid nitrogen cold plate, and after the temperature measuring point on the stationary plate cover plate drops and stabilizes, different powers are applied to the heating plate on the moving plate, and the thermal conductivity is calculated by the temperature difference between the stationary plate cover plate and the moving plate. By changing the material of the balls, we can verify the thermal conductivity of different materials. By changing the number of balls, we can verify the thermal conductivity of different contact areas.

6. The motion heat transfer test method for spacecraft vacuum thermal testing according to claim 5, characterized in that, include: The contact area is adjusted by adjusting the size of the stationary plate and the number of grooves in the ball bearings; The magnitude of prestress during the motion can be changed by adjusting the counterweight on the moving plate.

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